RU2360332C2 - Method of power supply of spacecraft with electrochemical generators during flight - Google Patents

Abstract

FIELD: chemistry; space technology; power engineering.

SUBSTANCE: invention relates to space technology and particularly to methods of power supply of spacecrafts (SC) with the power supply system based on electrochemical generators during a flight. According to the invention method includes generation of electric energy based on chemical reaction O₂ and H₂. Notably, that before derivation of initial chemical components O₂ and H₂ on a board of SC for energy generation ends, SC is joined in orbit to space energy platform with electrolytic section, water is pumped into it - reaction product of ECG SC, and after water electrolysis on the platform, SC is supplied with products of water electrolysis - chemical components O₂ and H₂ for further electrochemical reaction in ECG on the board of SC, thereafter SC is undocked from the platform and place into working orbit, the cycle is repeated required number of times.

EFFECT: extension of time for energy generation without increasing mass of initial chemical components O₂ and H₂ on the board of spacecraft, increase of electric power level without multiple increase of power supply system mass.

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Description

The invention relates to the space field and, in particular, to methods of power supply in flight of spacecraft (SC) with a power supply system based on electrochemical generators (ECG).

The prototype of the proposed method of power supply can serve as a known method of power supply in flight of the spacecraft using electrochemical generators [1]. Oxygen and hydrogen are usually used as reactive working substances in ECG. The specific gravity of ECG is about 20 kg / kW, and the specific consumption of fuel and oxidizing agent is about 0.4 kg / kW · h [1]. For example, to provide an electric power of 4 kW for 240 hours, the required mass of the ECG together with the O ₂ and H ₂ components will be about 460 kg. To ensure the energy consumption of the Clipper ship during 10 days of flight (average daily energy consumption of 2.5 kW) - about 290 kg [2].

The disadvantage of this method is that the ECG does not allow recharging, the stock of working substance in them is used once.

The objective of the invention is to increase the duration of electricity generation without increasing the mass of the initial chemical components O ₂ and H ₂ on board the spacecraft, increasing the level of electric power without a multiple increase in the mass of the power supply system.

This problem is solved by the fact that in the method of power supply in flight of a spacecraft with electrochemical generators, including generating electricity based on the chemical reaction of O ₂ and H ₂ , before the end of the production of the initial chemical components O ₂ and H ₂ on board the spacecraft to produce electricity, the spacecraft dock in orbit to a space energy platform with an electrolyzer, pump water into it - the product of a chemical reaction of electrochemical generators of a spacecraft; after water electrolysis, the platform is equipped with a spacecraft docked with the space energy platform, water electrolysis products are supplied with the chemical components O ₂ and H ₂ for the subsequent electrochemical reaction in electrochemical generators on board the spacecraft; undock the spacecraft from the platform and put it into working orbit; this cycle is repeated as many times as necessary.

The drawing shows a diagram illustrating the proposed method, where

1 - space energy platform with an electrolyzer;

2 - spacecraft (SC) with electrochemical generators.

The essence of the proposed method of energy supply in flight of a spacecraft with ECG is the generation of electricity based on the chemical reaction O ₂ and H ₂ , which consists in the fact that before the end of the production of the initial chemical components O ₂ and H ₂ on board the spacecraft 2, the spacecraft 2 are docked in orbit to the space energy platform with electrolyzer 1, water is pumped into it - the product of the chemical reaction of ECG KA 2; after electrolysis of water on platform 1, the spacecraft 2 is docked, docked with the space energy platform 1, water electrolysis products are supplied with the chemical components O ₂ and H ₂ for the subsequent electrochemical reaction in the ECG on board the spacecraft 2; undock the spacecraft 2 from the space energy platform 1 and put it into working orbit; This cycle is repeated as many times as necessary.

Thus, the duration of electricity generation is increased without increasing the mass of the initial chemical components O ₂ and H ₂ on board the spacecraft. Since the process of converting the chemical components O ₂ and H ₂ into water with the generation of electricity and the electrolytic decomposition of water into components

O ₂ and H ₂ can be repeated many times, then only the resource of technical devices can serve as a limitation on the number of conversion cycles.

Also, using this method of energy supply, it is possible to increase the average daily electric power produced by the energy supply system without a multiple increase in the mass of the system, reducing the duration of the flight without recharging. For example, the power supply system was designed for an average daily power of 4 kW. The specific gravity of the ECG is about 20 kg / kW, thus the mass of the ECG is approximately 80 kg. It is required to double the average daily power, for this the mass of the ECG increases and becomes approximately 160 kg, and the mass of the chemical components remains the same due to the reduction of the flight time without recharging. The total mass of the energy supply system rises by 17.4% and becomes equal to about 540 kg.

We explain the feasibility of using this method by examples. This method of energy supply can be used for spacecraft intended for work requiring microgravity conditions, for example, spacecraft for the production in space of materials with unique properties and biological products, and in this regard requiring large energy consumption for a long time. In this case, it is necessary to maintain a given level of microgravity (modern requirements for the microgravity situation on board the spacecraft, for work requiring the microgravity conditions, indicate the need to tighten the requirements for the level of microgravity environment to values of 10 ^-7 g _o [5], [6], [7 ]).

The use of rechargeable batteries for these purposes is impractical, since rechargeable batteries (AB), in comparison with ECG, have a low specific energy consumption [1], [3], [4]. To provide electric power of 4 kW for 240 hours, the required mass of the battery will be at least 6400 kg.

Solar batteries (SB) require the orientation of the SB panels in the sun to ensure maximum current collection (maximum current collection is achieved when sunlight is incident on the SB panel at an angle of 90 degrees). Maintaining a constant orientation leads to a deterioration of the microgravity situation onboard the spacecraft, for example, for Progress TGK in flight mode with stabilization by swirling around the axis of the SB direction to the Sun, the level of microgravity can reach values of ~ 4.5 · 10 ^-4 g _o .

The same drawback is characteristic of solar concentrators with thermal electrical conversion. In addition, a significant contribution to the deterioration of the microgravity situation onboard the spacecraft will be made by the operation of the turbine and compressor, integral elements of the process of converting thermal energy into electrical energy using a heat engine.

Nuclear facilities have shortcomings, mainly related to safety requirements. Creating screens that protect astronauts and equipment from radioactive penetrating radiation will greatly complicate the installation. Dynamic maneuvers for approaching and docking with a spacecraft carrying a nuclear power plant will not be easy. Hard nuclear radiation can cause irreversible negative changes in the cosmonauts' organisms and have a harmful effect on the technological processes of materials production (occurrence of structural defects in crystals, deterioration in the quality of biologically active preparations, etc.) [1].

With the proposed method of power supply in spacecraft flight, the power supply system during the spacecraft autonomous flight does not affect the level of microgravity conditions, since during the electrochemical reaction there is no force impact on the spacecraft, however, it provides a high level of electric power for a long time.

This method of energy supply can also be used for reusable manned spacecraft using aerodynamic drag in planetary atmospheres. For example, to solve the target problem, it is required to double the duration of the autonomous flight of a reusable transport manned spacecraft (MTPKK) of the Clipper type. To do this, the supply of components of the life support system is doubled, and the supply of chemical components of the energy supply system remains unchanged, since their quantity, during production, can be replenished during docking with the energy platform.

The placement for this purpose at the MPTSK Clipper SB is inexpedient, since it is impossible to completely protect the structural components of the SB from aerodynamic and heat flows during aerodynamic drag and launch of the spacecraft into near-planet orbit, which may lead to their partial or complete destruction, loss of performance, and damage to the design of the spacecraft itself. Also, the structural elements of the SB will adversely affect the aerodynamic quality of the ship, which can increase the amount of overload during aerodynamic braking, and make landing on the airfield impossible.

Another example: it is required for a long time to provide electric power to a reusable manned spacecraft designed to transport the crew between near-Earth and near-moon orbits based on the Clipper-type MTPKK. This spacecraft performs braking in the Earth’s atmosphere to the first space velocity and docked with a near-Earth orbital station, where the crew transfers to the Clipper type MTPKK and departs for the Earth. A new crew enters the interorbital manned spacecraft, which is sent to solve near-moon orbit to solve targets. Landing of this spacecraft is not provided. To increase the duration of the power supply system of this spacecraft can be through the proposed method of power supply. That is, after docking with a near-Earth orbital station, the interorbital manned spacecraft docked with the space energy platform, where it replenishes the supply of chemical components for the operation of ECG. The construction of the power supply system of this spacecraft on the basis of the SB is impractical for the above reasons.

This method of power supply can also be used for manned spacecraft intended for flights outside the asteroid belt, for example, to study Jupiter satellites delivered to near-Jupiter orbit using an interplanetary expeditionary complex equipped with a nuclear power plant. It is possible to increase the duration of the power supply system of this spacecraft using the proposed method of power supply, where an interplanetary expeditionary complex with a nuclear power plant will act as a space energy platform. The construction of the power supply system of this spacecraft on the basis of the SB is impractical, since the average distance from the Sun to Jupiter is approximately 778 million km, which is approximately 5.19 times the distance from the Sun to the Earth. This means that in order to obtain the same electrical power in the orbit of Jupiter as in the Earth’s orbit, it will be necessary to increase the area of SB panels by more than 26 times.

List of references

1. Avduevsky B.C., Leskov L.V. Weightlessness works. - M .: Young Guard, 1988. S.164-171.

2. Bruchanov N.A. The Clipper Project. - M.: “Cosmonautics News” No. 7, 2005, p.5.

3. Koroteev A.S., Koshelyaev E.M., Reshmin A.I. Space power today and tomorrow. - M.: Proceedings of the Academy of Sciences. Energy No. 5, 2001. S.3-16.

4. Kozlov D.I., Anshakov G.P., Agarkov V.F. and others. Design of automatic spacecraft. - M.: Mechanical Engineering, 1996. S.364-377.

5. Zemskov B.C., Belokurova I.N., Raukhman M.R., Shalimov V.P. The heterogeneity of the distribution of components in the cross sections of crystals grown by the Bridgman method in space flight is the result of the gravitational sensitivity of the melt (review of the works of IMET RAS). // Abstracts. VII Symposium “Mechanics of weightlessness. Results and prospects of fundamental research of gravitationally sensitive systems. ” April 11-14, 2000, M., Ed. IPMech. S.70-72.

6. Zemskov B.C. The concept of a space system for high technology in extremely low gravity. // Abstracts of the II Russian Conf. on space materials science (KM-2003). - Kaluga: Research Center for Space Materials Science, June 2003, p. 56.

7. Zharikov E.V., Senchenkov A.S., Egorov A.V. Low-energy methods for controlling the processes of mass transfer in the production of materials in space. // Abstracts of the II Russian Conf. on space materials science (KM-2003). - Kaluga: Research Center for Space Materials Science, June 2003, p.26.

Claims (1)

A method of power supply in flight of a spacecraft with electrochemical generators, including generating electricity based on the chemical reaction of O ₂ and H ₂ , characterized in that before the end of the production of the initial chemical components O ₂ and H ₂ on board the spacecraft to produce electricity, the spacecraft is docked in orbit to a space energy platform with an electrolyzer, water is pumped into it - the product of a chemical reaction of electrochemical generators of a spacecraft; after water electrolysis, the platform is equipped with a spacecraft docked with the space energy platform, water electrolysis products are supplied with the chemical components O ₂ and H ₂ for the subsequent electrochemical reaction in electrochemical generators on board the spacecraft; undock the spacecraft from the platform and put it into working orbit; this cycle is repeated as many times as necessary.